Aircraft fuel ice capturing filter housing, aircraft fuel ice capturing filter device, and method of use

ABSTRACT

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

BACKGROUND OF THE INVENTION

Ice can be present in aircraft fuel, e.g., when moisture accumulates inan aircraft fuel tank and the moisture freezes into ice when the tank isexposed to cold conditions, for example, when the aircraft is flying ataltitude. In some cases, the amount of ice (e.g., ice crystals) in thefuel can impact flow of the fuel through the aircraft fuel-oil heatexchanger, and even if the system bypasses fuel around the heatexchanger if clogged with ice, ice can impact flow through the aircraftfuel filter, and ice getting into sensitive fuel controls which meterthe amount of fuel into the aircraft engine can interrupt or adverselyaffect performance of the aircraft engine.

There is a need for improved fuel filter devices for removing ice fromaircraft fuel.

The present invention provides for ameliorating at least some of thedisadvantages of the prior art. These and other advantages of thepresent invention will be apparent from the description as set forthbelow.

BRIEF SUMMARY OF THE INVENTION

An embodiment of the invention provides an aircraft fuel ice capturingfilter device housing comprising (a) an aircraft fuel inlet; (b) anaircraft fuel outlet; (c) a main housing body receiving a flow ofaircraft fuel from the aircraft fuel inlet, the main housing bodycomprising a cylindrical element having a central cavity, an innersurface, an outer surface, and a vertical axis; and, (d) a cylindricalhollow insert contacting the inner surface of the main housing body, thecylindrical hollow insert having a plurality of spaced-apartice-capturing filters, each of the plurality of spaced-apartice-capturing filters having a front end, a rear end, a top wall, afirst side, a second side, a bottom opening, and a plurality ofapertures passing through the top wall, wherein the top wall at thefront end of each of the plurality of spaced-apart ice-capturing filtersis raised a distance from the inner surface of the cylindrical element,forming an opening arranged normal to aircraft fuel flow; wherein theaircraft fuel inlet is arranged generally perpendicular to the verticalaxis of the cylindrical element and is configured to provide tangentialaircraft fuel flow around the cylindrical element and the cylindricalinsert; and, wherein the cylindrical insert in the main housing body isconfigured to receive an aircraft fuel filter comprising a porousaircraft fuel filter element.

An aircraft fuel ice capturing filter device according to an embodimentof the invention comprises an embodiment of the aircraft fuel icecapturing filter device housing, wherein the aircraft fuel inlet and theaircraft fuel outlet define a fluid flow path though the aircraft fuelice capturing filter device housing, and the aircraft fuel ice capturingfilter device further comprises an aircraft fuel filter comprising aporous aircraft fuel filter element arranged in the housing across thefluid flow path.

In accordance with another embodiment of the invention, a method forfiltering aircraft fuel is provided, the method comprising passingaircraft fuel through an embodiment of the aircraft fuel ice capturingfilter device, wherein a portion of the aircraft fuel passes through theapertures of the plurality of spaced-apart ice-capturing filters.

In a preferred embodiment of the method, the aircraft fuel includes ice,and the method includes capturing ice in the plurality of spaced-apartice-capturing filters.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING(S)

FIG. 1A is a top isometric view of an illustrative aircraft fuel icecapturing device housing body (wherein the top cover has been removed)including an aircraft fuel inlet and a cylindrical insert comprising aplurality of spaced-apart ice-capturing filters according to anembodiment of the invention, also showing a cutout in the insert alignedwith a cut out in the cylindrical element for aircraft fuel inlet flow;FIG. 1B is a top isometric view of an illustrative aircraft fuel icecapturing device housing body without the cylindrical insert.

FIG. 2A is an isometric view of the insert (rolled to form a cylinder)with the plurality of spaced-apart ice-capturing filters, also showingthe cutout for aircraft fuel inlet flow; FIG. 2B is a top view of therolled insert shown in FIG. 2A.

FIGS. 3A-3D are views of an individual ice filter according to anembodiment of the invention. FIG. 3A shows a top view; FIG. 3B is asection view along line B-B of FIG. 3A, also showing a front upwardlyangled lip; FIG. 3C is an isometric view; and FIG. 3D is a bottom view.

FIG. 4A is an isometric side view of an assembled aircraft fuel icecapturing device comprising the housing and an aircraft fuel filter,showing the aircraft fuel ice capturing device housing top cover, theaircraft fuel inlet, the aircraft fuel outlet, and a portion of thefilter; FIG. 4B shows a top perspective view of the device; FIG. 4Cshows a top view; FIG. 4D shows a section view along line A-A of FIG.4C, also showing a hollow cylindrical aircraft fuel filter; FIG. 4Eshows a section view along line C-C of FIG. 4D, also showing hollowcylindrical aircraft fuel filter is a pleated filter; and FIG. 4F is apartial cut away view of the pleated filter, also showing an inner coreand an outer wrap.

FIGS. 5A-5C are external views of another aircraft fuel ice capturingdevice, also showing the aircraft fuel inlet and the aircraft fueloutlet. FIG. 5A is an isometric side view; FIG. 5B is a front view; andFIG. 5C is a bottom view.

FIG. 6 is a photograph of a tested aircraft fuel ice capturing insertshowing the ice captured by the plurality of spaced-apart ice-capturingfilters.

DETAILED DESCRIPTION OF THE INVENTION

An embodiment of the invention provides an aircraft fuel ice capturingfilter device housing comprising (a) an aircraft fuel inlet; (b) anaircraft fuel outlet; (c) a main housing body receiving a flow ofaircraft fuel from the aircraft fuel inlet, the main housing bodycomprising a cylindrical element having a central cavity, an innersurface, an outer surface, and a vertical axis; and, (d) a cylindricalhollow insert contacting the inner surface of the main housing body, thecylindrical hollow insert having a plurality of spaced-apartice-capturing filters, each of the plurality of spaced-apartice-capturing filters having a front end, a rear end, a top wall, afirst side, a second side, a bottom opening, and a plurality ofapertures passing through the top wall, wherein the top wall at thefront end of each of the plurality of spaced-apart ice-capturing filtersis raised a distance from the inner surface of the cylindrical element,forming an opening arranged normal to aircraft fuel flow; wherein theaircraft fuel inlet is arranged generally perpendicular to the verticalaxis of the cylindrical element and is configured to provide tangentialaircraft fuel flow around the cylindrical element and the cylindricalinsert; and, wherein the cylindrical insert in the main housing body isconfigured to receive an aircraft fuel filter comprising a porousaircraft fuel filter element.

An aircraft fuel ice capturing filter device according to an embodimentof the invention comprises an embodiment of the aircraft fuel icecapturing filter device housing, wherein the aircraft fuel inlet and theaircraft fuel outlet define a fluid flow path though the aircraft fuelice capturing filter device housing, and the aircraft fuel ice capturingfilter device further comprises an aircraft fuel filter comprising aporous aircraft fuel filter element arranged in the housing across thefluid flow path.

An embodiment of the invention provides an aircraft fuel ice capturingfilter device comprising an aircraft fuel ice capturing filter devicehousing comprising (a) an aircraft fuel inlet; (b) an aircraft fueloutlet; (c) a main housing body receiving a flow of aircraft fuel fromthe aircraft fuel inlet, the main housing body comprising a cylindricalelement having a central cavity, an inner surface, an outer surface, anda vertical axis; and, (d) a cylindrical hollow insert contacting theinner surface of the main housing body, the cylindrical hollow inserthaving a plurality of spaced-apart ice-capturing filters, each of theplurality of spaced-apart ice-capturing filters having a front end, arear end, a top wall, a first side, a second side, a bottom opening, anda plurality of apertures passing through the top wall, wherein the topwall at the front end of each of the plurality of spaced-apartice-capturing filters is raised a distance from the inner surface of thecylindrical element, forming an opening arranged normal to aircraft fuelflow; wherein the aircraft fuel inlet is arranged generallyperpendicular to the vertical axis of the cylindrical element and isconfigured to provide tangential aircraft fuel flow around thecylindrical element and the cylindrical hollow insert; wherein thecylindrical hollow insert in the cylindrical element is configured toreceive an aircraft fuel filter comprising a porous aircraft fuel filterelement; and, an aircraft fuel filter comprising a porous aircraft fuelfilter element arranged in the housing.

In accordance with another embodiment of the invention, a method forfiltering aircraft fuel is provided, the method comprising passingaircraft fuel through an embodiment of the aircraft fuel ice capturingfilter device, wherein a portion of the aircraft fuel passes through theapertures of the plurality of spaced-apart ice-capturing filters.

In a preferred embodiment of the method, the aircraft fuel includes ice,and the method includes capturing ice in the plurality of spaced-apartice-capturing filters.

In some embodiments of the method, the method further includes passingmelted ice through the outlet of the aircraft fuel ice capturing filterdevice.

Advantageously, smaller filters and filter devices can be utilized sincethe filters do not need to be designed for ice holding capacity, thusproviding for a reduced footprint and reduced weight.

Filters and filter devices according to the invention capture ice undermultiple conditions, including the current industry standard, AircraftFuel System and Component Icing Test SAE ARP1401B (Jun. 6, 2012),including the water concentration tests “Emergency System Operation” at288 ppm total water, and “Filter with Bypass Function Operation” whichis 2 cc/gallon above water saturation at 85±5° F.

Each of the components of the invention will now be described in moredetail below, wherein like components have like reference numbers.

FIG. 1A shows an embodiment of the aircraft fuel ice capturing devicehousing 1000 including an aircraft fuel inlet 1; an aircraft fuel outlet2; a main housing body 10 and a cylindrical insert 20 comprising aplurality of spaced-apart ice-capturing filters 100 arranged in the mainhousing body (FIG. 1B shows the main housing body without thecylindrical insert). The main housing is adapted for receiving a flow ofaircraft fuel from the aircraft fuel inlet, wherein the main housingbody (or bowl) 10 comprises a cylindrical element having a centralcavity 11, an inner surface 12, an outer surface 13, and a vertical axisA-A. As shown in FIG. 1A, the cylindrical hollow insert 20 with theplurality of spaced-apart ice-capturing filters has a central cavity 21,an insert inner surface 22, and an outer surface 23, wherein the outersurface 23 of the insert contacts the inner surface 12 of thecylindrical element, and the insert includes a cutout 25 for incomingaircraft fuel (shown in more detail in FIG. 2A).

As will be discussed in more detail below with respect to FIGS. 2A and3C, the insert includes spaced-apart cutouts 101 passing through theinner and outer surfaces 22, 23, wherein the spaced-apart cutouts 101and the exposed associated portions of the inner surface 12 of the mainhousing body 10 provide the bases of the ice capture filters 100, suchthat ice capture pockets 102 are provided.

The aircraft fuel inlet 1 (including a cut out providing a port passingthrough the inner surface 12, the cut out aligning with cut out 25 inthe cylindrical hollow insert) is arranged generally perpendicular tothe vertical axis of the cylindrical element and is configured toprovide tangential aircraft fuel flow around the inner surfaces of thecylindrical hollow insert/cylindrical element; and, wherein thecylindrical element and contained cylindrical hollow insert areconfigured to receive an aircraft fuel filter 200 comprising a porousaircraft fuel filter element 201 to provide an aircraft fuel icecapturing device 2000 (see FIGS. 4D and 4E).

In some embodiments, the aircraft fuel inlet 1 is configured to providetangential aircraft fuel flow around the cylindrical hollowinsert/cylindrical element of at least about 0.55 m/s when thetangential fuel inlet inner diameter is about 2 inches. As would berecognized by one of skill in the art, smaller aircraft engines normallyhave lower fuel flow rates and inlet diameters would decrease tominimize the size and weight of the system. Advantageously, thetangential flow at the inlet imparts a high velocity fluid rotation,forcing the aircraft fuel to the inner surfaces 12 and 22 of thecylindrical element and cylindrical hollow insert. Since ice and waterhave a higher density than that of aircraft fuel, the tangential flow atthe inlet allows for centrifugal separation of the ice/water from theaircraft fuel.

As shown in FIGS. 3A-3D, each of the plurality of spaced-apartice-capturing filters 100 is arranged on the inner surface of the mainhousing body, and each ice filter has a front end 105, a rear end 106, atop wall 107, a first side 108A, a second side 108B, and a bottomopening (cut-out 101), and a plurality of apertures 110 passing throughat least the top wall (in these Figures the apertures also pass throughthe rear end and first and second sides), wherein the top wall at thefront end of each of the plurality of spaced-apart ice-capturing filtersface is raised a distance from the inner surface 12 of the main housingbody 10, forming an opening 102A arranged normal to incoming aircraftfuel flow.

Preferably, individual ice-capturing filters have a minimum length (fromfront end 105 to rear end 106) of about 0.21 inches (about 5.3 mm), aminimum height (from surface 12 to the front end 105 of the top wall107) of about 0.21 inches (about 5.3 mm), a minimum width (from thefirst side 108A to the second side 108B) of about 0.22 inches (about 5.6mm). Typically, the opening 102A is at least about 0.20 inches (about 5mm).

The individual ice-capturing filters are spaced apart. As a result, flowenters the housing and is split into areas with ice capture and withoutice capture. Areas without ice capture devices will reduce changes invelocity as the flow spins tangentially around the inside of thecylindrical hollow insert/cylindrical element. Spacing the ice-capturingfilters apart at the upper part of the housing also avoids ice bridgingbetween ice-capturing filters which could block fuel flow (see FIG. 6 ,illustrating an aircraft fuel filter insert after use in a test housing,showing no ice bridging between ice-capturing filters).

Preferably, individual ice-capturing filters have a maximum height basedon a predetermined gap G (see FIG. 3E) between the aircraft fuel filteroutside diameter (OD) and the cylindrical element inside diameter (ID),assuming that the aircraft fuel filter is concentric with thecylindrical element ID. Illustratively, if the cylindrical element ID is4 inches (about 102 mm), and the aircraft fuel filter OD is 3.5 inches(about 89 mm), the maximum ice filter height should be about 0.25 inches(about 6 mm) to prevent interference.

The presence of apertures 110 in each ice filter minimizes stagnationpressure at the aircraft fuel inlet 1. While FIGS. 2A and 3C illustratethe apertures as annular in shape, and arranged in parallel horizontalrows, the apertures can have other shapes and be arranged in otherconfigurations. For example, the apertures can be oval in shape, andwith the ovals arranged vertically, horizontally, or at an angle. Anindividual aperture can extend from the front end to the rear end orfrom the first side to the second side. The filters can have apertureswith combinations of shapes. Typically, an individual aperture has amaximum diameter of 0.125 inches (about 3.2 mm), and preferably has asmaller diameter of about 0.010 inches (about 0.3 mm). The depth of theindividual apertures is typically equal to the thickness of the insertsheet, e.g., in the range of from about 0.01 inches (about 0.3 mm) toabout 0.04 inches (about 1 mm).

In some embodiments, as shown in FIGS. 3B and 3C, individualice-capturing filters have at the front end 105, a front upwardly angledlip 105A. In those embodiments wherein the ice filter has the frontupwardly angled lip, the lip is typically arranged at an angle in therange of from about 5° to about 45° from a horizontal axis defined bythe non-angled portion of the top wall. Without being bound to anyparticular theory, it is believed that the lip can assist in maintainingice flow velocity through the ice filter while increasing theprobability of ice capture.

An aircraft fuel filter 200 and aircraft fuel filter element 201 canhave any suitable pore structure, e.g., a pore size (for example, asevidenced by bubble point, or by KL as described in, for example, U.S.Pat. No. 4,340,479, or evidenced by capillary condensation flowporometry), a pore rating, a pore diameter (e.g., when characterizedusing the modified OSU F2 test as described in, for example, U.S. Pat.No. 4,925,572), or removal rating that reduces or allows the passagetherethrough of one or more materials of interest as the fluid is passedthrough the element.

The aircraft fuel filter can include additional elements, layers, orcomponents, that can have different structures and/or functions, e.g.,at least one of any one or more of the following: prefiltration,support, drainage, spacing and cushioning. Illustratively, the aircraftfuel filter can also include at least one additional element such as acore, mesh and/or a screen. In the embodiment shown in FIG. 4F, thefilter has an inner core and an outer wrap.

In accordance with embodiments of the invention, the aircraft fuelfilter comprises at least one porous aircraft fuel filter element. Theaircraft fuel filter element typically comprises a fibrous medium. Theaircraft fuel filter and/or the aircraft fuel filter element can have avariety of configurations, including pleated, and hollow cylindrical. Inone preferred embodiment, as shown in FIGS. 4D-4F the aircraft fuelfilter has a hollow cylindrical pleated configuration.

Any housing of suitable shape, providing an inlet and an outlet and acavity for an insert and aircraft fuel filter may be employed. FIGS. 4A,4B, and 5A-5C illustrate a variety of illustrative housings.

Each of the housings has, as described with respect to the embodimentshown in FIG. 1B, an aircraft fuel inlet; and an aircraft fuel outlet;and a main housing body comprising a cylindrical element having acentral cavity suitable for receiving a cylindrical insert comprising aplurality of spaced-apart ice-capturing filters (as described above,e.g., with respect to FIG. 2A), wherein the aircraft fuel inlet isarranged generally perpendicular to the vertical axis of the cylindricalelement and is configured to provide tangential aircraft fuel flowaround the inner surface of the hollow cylindrical element/cylindricalelement, and an aircraft fuel filter comprising a porous aircraft fuelfilter element can be arranged in the housing within the insert.

Using FIGS. 4A-4F for reference, an aircraft fuel filter 200 is disposedin the aircraft fuel ice capturing device housing 1000 within the cavity21 of the insert 20, the housing 1000 comprising the inlet 1 and theoutlet 2 and defining an aircraft fuel fluid flow path between the inletand the outlet, wherein the aircraft fuel filter 200 is across theaircraft fuel fluid flow path, to provide an aircraft fuel ice filterdevice 2000.

The housing and insert can be fabricated from any suitable rigidimpervious material (e.g., common aerospace metals and polymers), whichis compatible with the aircraft fuel being filtered. For example, thehousing can be fabricated from a metal or metal alloy, such as aluminum,magnesium, stainless steel, or from a composite including metal. Ifdesired, the housing can be manufactured by, for example, billet,casting, forging, additive manufacturing, extrusion, and lightpolymerization.

For example, the housing can monolithic, manufactured via additivemanufacturing (sometimes referred to as “additive layer manufacturing”or “3D printing”), typically formed by repeated depositions of a metalpowder bound together with an activatable binder (e.g., binder jetting,sometimes referred to as “drop on powder”), typically followed byagglomerating the powder, e.g., by sintering. Other suitable methodsinclude extrusion (e.g., paste extrusion, fused filament fabrication andfused deposition modelling) and light polymerization (e.g.,stereolithography apparatus (SLA), and digital light processing (DLP)).

Any suitable additive manufacturing equipment can be used, and a varietyof production 3D printers are suitable and commercially available.

The following example further illustrates the invention but, of course,should not be construed as in any way limiting its scope.

EXAMPLE

This example demonstrates capturing ice using an aircraft fuel icecapturing insert in a test housing according to an embodiment of theinvention.

An aircraft fuel ice capturing insert as generally shown in FIG. 2A isplaced in a transparent test housing, wherein the test housing containsa spiral nose cone with spiral grooves made from ultra high molecularweight polyethylene to create centrifugal force and a flow vector in thedirection of the ice filter openings. The insert is a sheet of aluminum6061 having a thickness of 0.032 inches (about 0.8 mm) with aperturediameters of 0.032 inches (about 0.8 mm) spaced on the sheet in astaggered hole pattern of 0.074 inches (about 1.9 mm), spaced at 0.074inches (about 1.9 mm) center to center.

The test housing is primed with aircraft fuel that does not contain ice.Aircraft fuel containing ice at a temperature of 27-33° F. is passedthrough the test device at a flow rate of 8 GPM, wherein the fuelaccelerates radially by traveling through the nose cone spiral grooves(the spiral grooves imparting rotation of fuel flow). During the test,the test housing is tilted at 45° from vertical to ensure that icecapture was not only due to the effects of gravity.

As seen through the transparent test housing, ice is uniformly capturedby the ice-capturing filters. As shown in FIG. 6 , ice is capturedwithout ice bridging between ice-capturing filters.

All references, including publications, patent applications, andpatents, cited herein are hereby incorporated by reference to the sameextent as if each reference were individually and specifically indicatedto be incorporated by reference and were set forth in its entiretyherein.

The use of the terms “a” and “an” and “the” and “at least one” andsimilar referents in the context of describing the invention (especiallyin the context of the following claims) are to be construed to coverboth the singular and the plural, unless otherwise indicated herein orclearly contradicted by context. The use of the term “at least one”followed by a list of one or more items (for example, “at least one of Aand B”) is to be construed to mean one item selected from the listeditems (A or B) or any combination of two or more of the listed items (Aand B), unless otherwise indicated herein or clearly contradicted bycontext. The terms “comprising,” “having,” “including,” and “containing”are to be construed as open-ended terms (i.e., meaning “including, butnot limited to,”) unless otherwise noted. Recitation of ranges of valuesherein are merely intended to serve as a shorthand method of referringindividually to each separate value falling within the range, unlessotherwise indicated herein, and each separate value is incorporated intothe specification as if it were individually recited herein. All methodsdescribed herein can be performed in any suitable order unless otherwiseindicated herein or otherwise clearly contradicted by context. The useof any and all examples, or exemplary language (e.g., “such as”)provided herein, is intended merely to better illuminate the inventionand does not pose a limitation on the scope of the invention unlessotherwise claimed. No language in the specification should be construedas indicating any non-claimed element as essential to the practice ofthe invention.

Preferred embodiments of this invention are described herein, includingthe best mode known to the inventors for carrying out the invention.Variations of those preferred embodiments may become apparent to thoseof ordinary skill in the art upon reading the foregoing description. Theinventors expect skilled artisans to employ such variations asappropriate, and the inventors intend for the invention to be practicedotherwise than as specifically described herein. Accordingly, thisinvention includes all modifications and equivalents of the subjectmatter recited in the claims appended hereto as permitted by applicablelaw. Moreover, any combination of the above-described elements in allpossible variations thereof is encompassed by the invention unlessotherwise indicated herein or otherwise clearly contradicted by context.

The invention claimed is:
 1. An aircraft fuel ice capturing filter device housing comprising: (a) an aircraft fuel inlet; (b) an aircraft fuel outlet; (c) a main housing body receiving a flow of aircraft fuel from the aircraft fuel inlet, the main housing body comprising a cylindrical element having a central cavity, an inner surface, an outer surface, and a vertical axis; and, (d) a cylindrical hollow insert contacting the inner surface of the main housing body, the cylindrical hollow insert having a plurality of spaced-apart ice-capturing filters, each of the plurality of spaced-apart ice-capturing filters having a front end, a rear end, a top wall, a first side, a second side, a bottom opening, and a plurality of apertures passing through the top wall, wherein the top wall at the front end of each of the plurality of spaced-apart ice-capturing filters is raised a distance from the inner surface of the cylindrical element, forming an opening arranged normal to aircraft fuel flow; wherein the aircraft fuel inlet is arranged perpendicular to the vertical axis of the cylindrical element and is configured to provide tangential aircraft fuel flow around the cylindrical element; and, wherein the cylindrical hollow insert in the main housing body is configured to receive an aircraft fuel filter comprising a porous aircraft fuel filter element.
 2. The aircraft fuel ice capturing filter device housing of claim 1, wherein each of the plurality of spaced-apart ice-capturing filters include a plurality of apertures passing through the first side and the second side.
 3. The aircraft fuel ice capturing filter device housing of claim 1, wherein the top wall at the front end of each of the plurality of spaced-apart ice filters includes an upwardly angled lip.
 4. An aircraft fuel ice capturing filter device comprising: the aircraft fuel ice capturing filter device housing of claim 1; and, an aircraft fuel filter comprising a porous aircraft fuel filter element arranged in the housing.
 5. A method of filtering aircraft fuel, the method comprising passing aircraft fuel through the aircraft fuel ice capturing filter device of claim
 4. 6. The method of claim 5, wherein the aircraft fuel includes ice, and the method includes capturing ice in the plurality of spaced-apart ice-capturing filters and allowing a portion of aircraft fuel to pass through the spaced-apart ice-capturing filters.
 7. The method of claim 5, further comprising further includes passing melted ice through the outlet of the aircraft fuel ice capturing filter device.
 8. The aircraft fuel ice capturing filter device housing of claim 2, wherein the top wall at the front end of each of the plurality of spaced-apart ice filters includes an upwardly angled lip.
 9. An aircraft fuel ice capturing filter device comprising: the aircraft fuel ice capturing filter device housing of claim 2; and, an aircraft fuel filter comprising a porous aircraft fuel filter element arranged in the housing.
 10. An aircraft fuel ice capturing filter device comprising: the aircraft fuel ice capturing filter device housing of claim 3; and, an aircraft fuel filter comprising a porous aircraft fuel filter element arranged in the housing.
 11. The method of claim 6, further comprising further includes passing melted ice through the outlet of the aircraft fuel ice capturing filter device. 